[Federal Register Volume 63, Number 168 (Monday, August 31, 1998)]
[Rules and Regulations]
[Pages 46160-46164]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-23095]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-SW-23-AD; Amendment 39-10725; AD 98-10-09]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model SA.315B,
SA.316B, SA.316C, SA.319B, and SE.3160 Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This document publishes in the Federal Register an amendment
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adopting Airworthiness Directive (AD) 98-10-09 which was sent
previously to all known U.S. owners and operators of Eurocopter France
Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160 helicopters by
individual letters. This AD requires an initial and recurring
inspections of the blade spar for cracks. This amendment is prompted by
an accident in which a Model SA.315B helicopter lost a main rotor
blade. The cause of the blade failure was fatigue cracking. This
condition, if not corrected, could result in separation of a blade and
subsequent loss of control of the helicopter.
DATES: Effective September 15, 1998, to all persons except those
persons to whom it was made immediately effective by priority letter AD
98-10-09, issued on May 6, 1998, which contained the requirements of
this amendment.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 15, 1998.
Comments for inclusion in the Rules Docket must be received on or
before October 30, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Regional Counsel, Southwest Region,
Attention: Rules Docket No. 98-SW-23-AD, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137.
The applicable service information may be obtained from American
Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-
4005, telephone (972) 641-3460, fax (972) 641-3527. This information
may be examined at the FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mr. Shep Blackman, Aerospace Engineer,
FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham
Blvd., Fort Worth, Texas 76137, telephone (817) 222-5296, fax (817)
222-5961.
SUPPLEMENTARY INFORMATION: On February 12, 1998, the FAA issued
priority letter AD 98-04-40 (FAA Docket 98-SW-09-AD), applicable to
Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160
helicopters. That AD was published in the Federal Register on April 17,
1998 (63 FR 19183). That AD requires, for blades with 400 or more hours
time-in-service (TIS), within 25 hours TIS, inspecting each blade spar
for cracks using a dye-penetrant method, and visually inspecting each
blade cuff for cracks using a 10-power or higher magnifying glass. If a
crack is discovered in either a blade spar or cuff, removal and
replacement of the blade with an airworthy blade is required prior to
further flight. That action was prompted by an accident in which a
Model SA.315B helicopter lost a main rotor blade (blade) just prior to
take-off. Although the main gearbox and the remainder of the main rotor
assembly separated from the helicopter and passed through the cockpit,
there were no fatalities. The cause of the blade failure was determined
to be fatigue cracks that originated from the outboard blade-to-cuff
attachment bolt hole and progressed through the blade spar and cuff.
That condition, if not corrected, could result in separation of a blade
and subsequent loss of control of the helicopter. Priority Letter AD
98-10-09 issued May 6, 1998, superseded AD 98-04-40. AD 98-10-09
requires the same one-time inspections as required by AD 98-04-40, but
also requires, at intervals not to exceed 25 hours TIS, a recurring
visual inspection of the blade spar at the outboard blade-to-cuff
attachment bolt hole for cracks using a 10-power or higher magnifying
glass.
The FAA has reviewed Eurocopter France Service Telex No. 00055/
0034/98, dated February 3, 1998 (Eurocopter Service Telex: 316/319 No.
01.64 and 315 No. 01.29), which describes procedures for inspecting
each blade spar for cracks using a dye-penetrant method, and visually
inspecting each blade cuff for cracks using a 10-power or higher
magnifying glass; and Eurocopter France Service Telex No. 00060/00099/
98, dated April 9, 1998 (Eurocopter Service Telex: 316/319 No. 01.65
and 315 No. 01.30), which describes procedures for repetitively
inspecting each blade spar for cracks using a 10-power or higher
magnifying glass. Additionally, the Direction Generale De L'Aviation
Civile, which is the airworthiness authority for France, has issued AD
98-088-055(A) and 98-089-038(A), both dated February 25, 1998; and AD
98-170-056(A)R1 and 98-171-039(A)R1, both dated May 6, 1998, to mandate
these actions.
Since the unsafe condition described is likely to exist or develop
on other Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B,
and SE.3160 helicopters of the same type design, the FAA issued
priority letter AD 98-10-09 to prevent separation of a blade and
subsequent loss of control of the helicopter. This AD requires, for
blades with 400 or more hours time-in-service (TIS), within 25 hours
TIS, inspecting each blade spar for cracks using a dye-penetrant
method, and visually inspecting each blade cuff for cracks using a 10-
power or higher magnifying glass; and thereafter, visually inspecting
each blade spar with a 10-power or higher magnifying glass at intervals
not to exceed 25 hours TIS. If a crack is discovered in either a blade
spar or cuff, removal and replacement of the blade with an airworthy
blade is required prior to further flight. The actions are required to
be accomplished in accordance with the service telexes described
previously.
Since it was found that immediate corrective action was required,
notice and opportunity for prior public comment thereon were
impracticable and contrary to the public interest, and good cause
existed to make the AD effective immediately by individual letters
issued on May 6, 1998 to all known U.S. owners and operators of
Eurocopter France Model SA.315B, SA.316B, SA.316C, SA.319B, and SE.3160
helicopters. These conditions still exist, and the AD is hereby
published in the Federal Register as an amendment to section 39.13 of
the Federal Aviation Regulations (14 CFR 39.13) to make it effective to
all persons. The FAA has made two non-substantive changes to the
Priority Letter AD which will neither increase the economic burden on
an operator nor increase the scope of the AD. The 400 or more hours TIS
threshold provision has been moved from the compliance paragraph to the
applicability paragraph. Additionally, Figure 1 has been enhanced to
provide a clearer picture of the affected blade area.
Previous completion of the inspections required by AD 98-04-40
constitutes compliance with the initial blade inspections required by
this AD. The recurring visual inspections specified in this AD shall
begin on or before 25 hours TIS after the initial inspections required
by either this AD or AD 98-04-40, whichever occurred first. If more
than 25 hours TIS has elapsed since the inspections required by AD 98-
04-40, then the recurring visual inspection specified in this AD must
be accomplished prior to further flight.
The FAA estimates that 106 helicopters of U.S. registry will be
affected by this AD, that it will take approximately 4 work hours per
helicopter to inspect a blade and 4 work hours to replace a main rotor
blade, if necessary, and that the average labor rate is $60 per work
hour. Required parts will cost approximately $49,700 per blade. Based
on these figures, the total cost impact of the AD on U.S. operators is
estimated to be $5,319,080
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for the first year, assuming one blade replacement per helicopter and
$25,440 each subsequent year, assuming five inspections per year and no
blade replacements.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 98-SW-23-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not have substantial direct
effects on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-10479 (63 FR
19183, April 17, 1998) and by adding a new airworthiness directive
Amendment 39-10725 to read as follows:
AD 98-10-09 Eurocopter France: Amendment 39-10725. Docket No. 98-
SW-23-AD. Supersedes AD 98-04-40, Amendment 39-10479, Docket 98-SW-
09-AD.
Applicability: Model SA.315B, SA.316B, SA.316C, SA.319B, and
SE.3160 helicopters, with main rotor blades, part numbers 3160S11-
10000 all dash numbers, 3160S11-30000 all dash numbers, 3160S11-
35000 all dash numbers, 3160S11-40000 all dash numbers, 3160S11-
45000 all dash numbers, 3160S11-50000 all dash numbers, or 3160S11-
55000 all dash numbers, with 400 or more hours time-in-service
(TIS), installed, certificated in any category.
Note 1: This AD applies to each helicopter identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For helicopters that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must use the authority
provided in paragraph (f) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition, or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any helicopter from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent separation of a blade and subsequent loss of control
of the helicopter, accomplish the following:
(a) Within 25 hours TIS, inspect each blade spar for cracks
using a dye-penetrant method in accordance with paragraphs CC.1
through CC.4 of the Operational Procedures in Eurocopter France
Service Telex No. 00055/0034/98, dated February 3, 1998 (Eurocopter
Service Telex: 316/319 No. 01.64 and 315 No. 01.29).
(b) Within 25 hours TIS, visually inspect the upper and lower
surfaces of each blade cuff for cracks, especially around the
attachment bolts, using a 10-power or higher magnifying glass.
(c) Within 25 hours TIS from the last required inspection of
each blade spar for cracks in the area indicated in Figure 1, and
thereafter at intervals not to exceed 25 hours TIS:
(1) Without removing the blade from the helicopter, clean each
blade root area using ``Teepol'' or an equivalent product.
(2) Support the blade tip to eliminate blade droop while
inspecting the lower blade surface.
(3) Visually inspect each blade spar with a 10-power or higher
magnifying glass along the hatched area indicated in Figure 1,
beginning on the blade lower surface, then on the flat section of
the trailing edge (B), on the blade upper surface, and then on the
flat section of the leading edge (A).
(4) Before returning the blades to service, confirm that there
is a sealing bead (1) around the edge of the blade cuff.
Note 2: Eurocopter France Service Telex No. 00060/00099/98,
dated April 9, 1998 (Eurocopter Service Telex: 316/319 No. 01.65 and
315 No. 01.30) pertains to the subject of this AD.
(d) If more than 25 hours TIS have elapsed since the last
required inspection of each blade spar for cracks in the area
indicated in Figure 1, before further flight, conduct the
inspections required by paragraph (c) of this AD.
(e) If a crack is found in a blade spar or cuff, remove the
blade and replace it with an airworthy blade prior to further
flight.
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(f) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Rotorcraft Standards Staff,
Rotorcraft Directorate, FAA. Operators shall submit their requests
through an FAA Principal Maintenance Inspector, who may concur or
comment and then send it to the Manager, Rotorcraft Standards Staff.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Rotorcraft Standards Staff.
(g) Special flight permits will not be issued.
(h) The inspection shall be done in accordance with paragraphs
CC.1 through CC.4 of the Operational Procedures in Eurocopter France
Service Telex No. 00055/0034/98, dated February 3, 1998. This
incorporation by reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. Copies may be obtained from American Eurocopter Corporation,
2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972)
641-3460, fax (972) 641-3527. Copies may be inspected at the FAA,
Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(i) This amendment becomes effective on September 15, 1998, to
all persons except those persons to whom it was made immediately
effective by Priority Letter AD 98-10-09, issued May 6, 1998, which
contained the requirements of this amendment.
Note 4: The subject of this AD is addressed in Direction
Generale De L'Aviation Civile (France) AD 98-088-055(A) and 98-089-
038(A), both dated February 25, 1998; and Direction Generale De
L'Aviation Civile (France) AD 98-170-056(A)R1 and 98-171-039(A)R1,
both dated May 6, 1998.
Issued in Fort Worth, Texas, on August 21, 1998.
Larry M. Kelly,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 98-23095 Filed 8-28-98; 8:45 am]
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